System for controlling variable-setting blades for a turbine engine
The invention relates to a system for controlling variable-setting blades ( 14 ) for a turbine engine, which includes at least one control ring ( 36 ) mounted rotatably mobile about an annular casing ( 16 ) with axis of revolution A, at least one annular row of variable-setting blades ( 14 ) extending substantially radially relative to said axis A and connected to said at least one control ring so that a rotation of the ring about the casing rotates the blades about substantially radial axes B, and means ( 40 ) for actuating said at least one ring in order to rotate same about the casing, characterised in that said actuation means are connected to said at least one ring by linking means comprising a shaft ( 52 ) extending along an axis C which is substantially radial relative to said axis A and mounted rotatably mobile about said axis C on the housing.
1. System for controlling variable pitch vanes for a turbine engine, comprising at least one control ring mounted to freely rotate about a first annular casing with an axis of revolution A, at least one annular row of variable pitch vanes extending substantially radially relative to said axis A and being connected to said at least one control ring so that a rotation of the ring about the first casing sets the vanes into rotation about substantially radial axes B, and means for actuating said at least one ring so as to rotate it about the first casing, said actuation means being connected to said at least one ring by linking means comprising a shaft extending along an axis C that is substantially radial relative to said axis A and is mounted to freely rotate about said axis C on the first casing, characterised in that said shaft comprises a radially internal end mounted on the first casing by a pivot link or ball joint link and a radially external end connected by a pivot link or ball joint link to a fixed arm rigidly connected to a second casing or to the first casing.
2. System according to claim 1 , wherein said shaft comprises a first clevis for linking, via a first tensioner, to a first control ring.
3. System according to claim 2 , wherein said shaft comprises a second clevis for linking, via a second tensioner, to a second control ring.
4. System according to claim 3 , wherein said shaft is located between said first and second control rings.
5. System according to claim 3 , wherein said first and second clevises are diametrically opposed relative to said axis C.
6. System according to claim 3 , wherein said first clevis or each of said first and second clevises supports an articulation shaft of the corresponding tensioner, which articulation shaft is substantially radial relative to said axis A.
7. System according to claim 1 , wherein said arm extends substantially parallel to said axis A.
8. System according to claim 1 , wherein said arm comprises a first longitudinal end for linking to said shaft and a second opposite longitudinal end for fixing to said second casing.
9. System according to claim 8 , wherein said second end comprises a plate for fixing to said second casing.
10. System according to claim 8 , wherein said second casing is an intermediate casing fixed to said first annular casing.
11. Turbine engine for aircraft, comprising at least one system according to claim 1 .